EP0717170A1 - Dispositif d'étanchéité pour la plate-forme des aubes du rotor de turbine - Google Patents

Dispositif d'étanchéité pour la plate-forme des aubes du rotor de turbine Download PDF

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Publication number
EP0717170A1
EP0717170A1 EP95309119A EP95309119A EP0717170A1 EP 0717170 A1 EP0717170 A1 EP 0717170A1 EP 95309119 A EP95309119 A EP 95309119A EP 95309119 A EP95309119 A EP 95309119A EP 0717170 A1 EP0717170 A1 EP 0717170A1
Authority
EP
European Patent Office
Prior art keywords
platforms
blades
root
gap
airfoil
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP95309119A
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German (de)
English (en)
Other versions
EP0717170B1 (fr
Inventor
William Kevin Barcza
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP0717170A1 publication Critical patent/EP0717170A1/fr
Application granted granted Critical
Publication of EP0717170B1 publication Critical patent/EP0717170B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

  • This invention applies to turbine engine rotor assemblies in general, and to apparatus for sealing between adjacent rotor blades within a turbine engine rotor assembly in particular.
  • Turbine and compressor sections within an axial flow turbine engine generally include a rotor assembly comprising a rotating disc and a plurality of rotor blades circumferentially disposed around the disc.
  • Each rotor blade includes a root, an airfoil, and a platform positioned in the transition area between the root and the airfoil.
  • the roots of the blades are received in complementary shaped recesses within the disc.
  • the platforms of the blades extend laterally outward and collectively form a flow path for the fluids passing through the turbine.
  • an apparatus for sealing a gap between adjacent blades in a rotor assembly for a gas turbine engine including a plurality of blades circumferentially disposed around a disc, each of the blades having an airfoil, a root, and a platform extending outward in a lateral direction in a transition area between the root and the airfoil, the gap being formed between edges of adjacent platforms, wherein the platforms collectively form a flow path for primary fluid flow passing by the airfoil side of the platforms and secondary fluid flow passing by the root side of the platforms, said apparatus comprising: a thin plate body, having a length and a width; means for conducting secondary flow between said thin plate body and root side surfaces of adjacent blade platforms, and thereafter into the gap; whereby in use said secondary flow travelling between said thin plate body and said root side surfaces may transfer thermal energy away from the platforms.
  • a rotor assembly for a gas turbine engine comprising:
  • a method for transferring thermal energy from the platforms of rotor assembly blades in a gas turbine engine comprising the steps of:
  • a rotor assembly comprising a plurality of blades mounted on a disc, each blade having an airfoil, a root and a platform, wherein a gap is formed between platforms of adjacent blades, said assembly also comprising a plurality of sealing means, each said sealing means being disposed between two blades, said assembly also comprising passage means for conducting flow between the sealing means and the adjacent platforms and through each gap.
  • An advantage of the preferred embodiments of the present invention is that platform cooling is provided without adding stress rising apertures in the platform.
  • a further advantage of the preferred embodiments of the present invention is that the heat transfer for a particular flow of secondary fluid is optimized.
  • secondary flow is drawn between the body of the seal and the root side surface of each platform before exiting through the gap.
  • the flow pattern between the two surfaces increases the heat transfer from the platforms to the secondary flow.
  • a still further advantage of the preferred embodiments of the present invention is that the means for transferring thermal energy from the platforms to the secondary fluid does so at minimal energy losses to the engine.
  • a still further advantage of the preferred embodiments of the present invention is that the platform cooling means of the present invention is considerably less expensive than prior art cooling means.
  • a turbine blade 10 is shown with an apparatus 12 for: (1) sealing gaps between adjacent blades 10 of a turbine blade rotor assembly; and (2) damping vibrations of adjacent blades 10.
  • the apparatus 12 includes a platform seal 14 and a damping block 16.
  • the platform seal 14 comprises a thin plate body having a width 18, and a length defined by a first end 22 and a second end 24.
  • the first end 22 of the platform seal 14 is formed into a hook shape.
  • the platform seal 14 further includes a plurality of channels 17.
  • the channels 17 are corrugations which extend across the width 18 of the seal 14.
  • the channels 17 may assume different paths from an outer edge to a centre region of the seal 14 and be formed by means other than corrugation.
  • the damping block 16 includes a body 26, a pair of flanges 28, a rod 30, and a windage surface 32.
  • the body 26 includes a pair of friction surfaces 34 for contacting adjacent blades 10 (see FIG. 3).
  • the flanges 28 are formed on opposite sides of the body 26 and each includes a section 36 extending out from the body 26.
  • the rod 38 is fixed between the flange sections 36 extending out from the body 26.
  • each turbine blade 10 includes an airfoil 40, a root 42, and a platform 44.
  • the platform 44 extends laterally outward in the transition area between the root 42 and the airfoil 40 and may be described as having an airfoil side 46, a root side 48, a width 50, and a length 52 extending from a forward edge 54 to a rearward edge 56.
  • the platform 44 includes a pair of locating surfaces 58, a seal pocket 60, and a damping shelf 62 for receiving a friction surface 34 of the damping block 16.
  • the locating surfaces 58 extend laterally outward from the lengthwise sides of the blade 10, on the root side 48 of the platform 44.
  • the seal pocket 60 is formed in the rearward portion of the platform 44, on the root side 48 of the platform 44, with the opening of the pocket 60 facing toward the forward edge 54.
  • the damping shelf 62 is formed in the forward section of the platform 44, also on the root side 48.
  • a section of a turbine blade rotor assembly 66 includes a pair of adjacent turbine blades 10 mounted in a disc 68.
  • the disc 68 includes a plurality of recesses 70 circumferentially distributed in the outer surface 72 of the disc 68 for receiving the roots 42 of the turbine blades 10.
  • FIG. 3 shows the roots 42 and recesses 70 having a conventional fir tree configuration.
  • the disc 68 further includes an annular slot 74 disposed in the outer surface 72 of the disc 68 for receiving damping blocks 16.
  • FIGS. 5 and 6 show the annular slot 74 from a side view.
  • the turbine blade rotor assembly 66 may be assembled by first joining the platform seals 14 and the damping blocks 16 as is shown in FIG. 3.
  • the rod 30 of the damping block 16 is received within the hook-shaped first end 22 of the platform seal 14 and the seal 14 is rotated into a position where the damping block 16 prevents the seal 14 and block 16 from disengaging.
  • a first turbine blade 10 is installed in the disc 68.
  • the coupled platform seal 14 and damping block 16 are placed within the annular slot 74 of the disc 68 and slid laterally into engagement with the installed blade 10.
  • the second end 24 of the platform seal 14 is received within the seal pocket 60 and the platform seal 14 is slid into contact with the lateral locating surfaces 58.
  • the second end 24 of the platform seal 14 is maintained in a particular radial position by the seal pocket 60;
  • the weight of the damper block 16 maintains the first end 22 of the platform seal 14 and the damper block 16 at the lowest radial position within the annular slot 74 (shown in FIG. 4); and (3) the lateral locating surfaces 58 maintain approximately one-half of the width 18 (see FIG.
  • the channels 17 within the platform seal 44 provide means for conducting secondary flow between the thin plate body of the platform seal 44 and the root side surfaces 19 of the platforms 44.
  • the flow may enter either side of the platform seal 44 width 18 and exit through the gap 21 between the platforms 44 (see FIG. 3) and into the primary flow.
  • the channels 17 may extend from any side of the platform seal 14 through to a central region of the seal 14 that is exposed to the gap 21 between the adjacent platforms 44.
  • the present invention has been heretofore described in terms of a plurality of channels 17 being formed in the platform seal 14 as a means for conducting secondary flow between the thin plate body of the platform seal 14 and the root side surfaces 19 of the adjacent platforms 44.
  • the channels 17 may be formed in the root side surfaces 19 of the platforms 44, as is shown in FIG. 5.
  • the channels 17 in the platform 44 extend laterally inward beyond the lateral locating surfaces 58 to ensure that the platform channels 17 are exposed to the secondary flow passing thereby.
  • the platform seal 14 has heretofore been described in terms of a seal coupled with a damping block.
  • the apparatus for sealing a gap between adjacent blades, having means for conducting secondary flow between the body and root side surfaces of adjacent blade platforms, and thereafter into the gap, may alternatively comprise seals other than those coupled with damping blocks.
  • the present invention provides a means for sealing between adjacent rotor blades, means for dissipating thermal energy within a blade platform, and means for reducing thermal stress within blade platforms, and that the preferred embodiments of the present invention dissipate thermal energy within the blade platforms without negatively affecting the efficiency of the engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP95309119A 1994-12-14 1995-12-14 Dispositif d'étanchéité pour la plate-forme des aubes du rotor de turbine Expired - Lifetime EP0717170B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US355800 1982-03-08
US08/355,800 US5513955A (en) 1994-12-14 1994-12-14 Turbine engine rotor blade platform seal

Publications (2)

Publication Number Publication Date
EP0717170A1 true EP0717170A1 (fr) 1996-06-19
EP0717170B1 EP0717170B1 (fr) 1999-03-10

Family

ID=23398901

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95309119A Expired - Lifetime EP0717170B1 (fr) 1994-12-14 1995-12-14 Dispositif d'étanchéité pour la plate-forme des aubes du rotor de turbine

Country Status (5)

Country Link
US (1) US5513955A (fr)
EP (1) EP0717170B1 (fr)
JP (1) JP3789153B2 (fr)
AU (1) AU704412B2 (fr)
DE (1) DE69508201T2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2055898A2 (fr) * 2007-11-02 2009-05-06 United Technologies Corporation Aube de turbine dotée de refroidissement de plate-forme
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Families Citing this family (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2726323B1 (fr) * 1994-10-26 1996-12-13 Snecma Ensemble d'un disque rotatif et d'aubes, notamment utilise dans une turbomachine
US5738490A (en) * 1996-05-20 1998-04-14 Pratt & Whitney Canada, Inc. Gas turbine engine shroud seals
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5803710A (en) * 1996-12-24 1998-09-08 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
FR2758855B1 (fr) * 1997-01-30 1999-02-26 Snecma Systeme de ventilation des plates-formes des aubes mobiles
US5820338A (en) * 1997-04-24 1998-10-13 United Technologies Corporation Fan blade interplatform seal
FR2810365B1 (fr) * 2000-06-15 2002-10-11 Snecma Moteurs Systeme de ventilation d'une paire de plates-formes d'aubes juxtaposees
US6431835B1 (en) 2000-10-17 2002-08-13 Honeywell International, Inc. Fan blade compliant shim
US6612809B2 (en) * 2001-11-28 2003-09-02 General Electric Company Thermally compliant discourager seal
US6932575B2 (en) * 2003-10-08 2005-08-23 United Technologies Corporation Blade damper
DE102004016174A1 (de) * 2004-03-30 2005-10-20 Alstom Technology Ltd Baden Spaltdichtung zum Abdichten eines Spalts zwischen zwei benachbarten Bauteilen
US7121800B2 (en) * 2004-09-13 2006-10-17 United Technologies Corporation Turbine blade nested seal damper assembly
US7207771B2 (en) * 2004-10-15 2007-04-24 Pratt & Whitney Canada Corp. Turbine shroud segment seal
US7597542B2 (en) * 2005-08-30 2009-10-06 General Electric Company Methods and apparatus for controlling contact within stator assemblies
US7766606B2 (en) * 2006-08-17 2010-08-03 Siemens Energy, Inc. Turbine airfoil cooling system with platform cooling channels with diffusion slots
EP1914036B1 (fr) * 2006-10-16 2010-03-03 Siemens Aktiengesellschaft Aube de turbine pour une turbine avec un canal de refroidissement
US7758306B2 (en) * 2006-12-22 2010-07-20 General Electric Company Turbine assembly for a gas turbine engine and method of manufacturing the same
US7794201B2 (en) * 2006-12-22 2010-09-14 General Electric Company Gas turbine engines including lean stator vanes and methods of assembling the same
RU2486349C2 (ru) * 2007-10-25 2013-06-27 Сименс Акциенгезелльшафт Уплотнительный гребень, узел лопаток турбины и газовая турбина, содержащая такой узел лопаток
US8137072B2 (en) * 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
PL2406464T3 (pl) 2009-03-09 2015-11-30 Ge Avio Srl Wirnik do maszyn wirnikowych
US8356978B2 (en) * 2009-11-23 2013-01-22 United Technologies Corporation Turbine airfoil platform cooling core
US8672626B2 (en) 2010-04-21 2014-03-18 United Technologies Corporation Engine assembled seal
US8790086B2 (en) 2010-11-11 2014-07-29 General Electric Company Turbine blade assembly for retaining sealing and dampening elements
FR2970033B1 (fr) * 2011-01-04 2015-10-16 Turbomeca Procede d'amortissement de pale de turbine a gaz et amortisseur de vibration de mise en oeuvre
US8734111B2 (en) * 2011-06-27 2014-05-27 General Electric Company Platform cooling passages and methods for creating platform cooling passages in turbine rotor blades
US10113434B2 (en) 2012-01-31 2018-10-30 United Technologies Corporation Turbine blade damper seal
US9279332B2 (en) 2012-05-31 2016-03-08 Solar Turbines Incorporated Turbine damper
US9650901B2 (en) 2012-05-31 2017-05-16 Solar Turbines Incorporated Turbine damper
US10253642B2 (en) * 2013-09-16 2019-04-09 United Technologies Corporation Gas turbine engine with disk having periphery with protrusions
EP3047112B1 (fr) * 2013-09-17 2018-11-14 United Technologies Corporation Turbine à gaz dotée d'un joint d'étanchéité présentant des saillies
GB201322668D0 (en) * 2013-12-20 2014-02-05 Rolls Royce Deutschland & Co Kg Vibration Damper
US10030530B2 (en) * 2014-07-31 2018-07-24 United Technologies Corporation Reversible blade rotor seal
US20160230579A1 (en) * 2015-02-06 2016-08-11 United Technologies Corporation Rotor disk sealing and blade attachments system
EP3088679A1 (fr) * 2015-04-30 2016-11-02 Rolls-Royce Corporation Joint pour ensemble de moteur de turbine à gaz
US10458264B2 (en) * 2015-05-05 2019-10-29 United Technologies Corporation Seal arrangement for turbine engine component
US9976427B2 (en) 2015-05-26 2018-05-22 United Technologies Corporation Installation fault tolerant damper
US10196915B2 (en) * 2015-06-01 2019-02-05 United Technologies Corporation Trailing edge platform seals
US9810087B2 (en) * 2015-06-24 2017-11-07 United Technologies Corporation Reversible blade rotor seal with protrusions
US9822658B2 (en) 2015-11-19 2017-11-21 United Technologies Corporation Grooved seal arrangement for turbine engine
EP3293353A1 (fr) 2016-09-13 2018-03-14 Siemens Aktiengesellschaft Technique d'équilibrage d'un rotor de compresseur d'une turbine à gaz
US10648362B2 (en) * 2017-02-24 2020-05-12 General Electric Company Spline for a turbine engine
US20180340437A1 (en) * 2017-02-24 2018-11-29 General Electric Company Spline for a turbine engine
US10941671B2 (en) * 2017-03-23 2021-03-09 General Electric Company Gas turbine engine component incorporating a seal slot
US10323520B2 (en) * 2017-06-13 2019-06-18 General Electric Company Platform cooling arrangement in a turbine rotor blade
US10907491B2 (en) * 2017-11-30 2021-02-02 General Electric Company Sealing system for a rotary machine and method of assembling same
US10982559B2 (en) * 2018-08-24 2021-04-20 General Electric Company Spline seal with cooling features for turbine engines
US11566528B2 (en) * 2019-12-20 2023-01-31 General Electric Company Rotor blade sealing structures
US11781440B2 (en) * 2021-03-09 2023-10-10 Rtx Corporation Scalloped mateface seal arrangement for CMC platforms

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2413542A1 (fr) * 1977-12-28 1979-07-27 Gen Electric Amortisseur d'aube de turbomachine
DE3236021A1 (de) * 1981-11-10 1983-05-19 BBC Aktiengesellschaft Brown, Boveri & Cie., 5401 Baden, Aargau Mit schaufeln versehener turbinenrotorkoerper
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
WO1994012772A1 (fr) * 1992-11-24 1994-06-09 United Technologies Corporation Joint d'etancheite pour aubes d'une turbine a gaz
FR2712629A1 (fr) * 1983-07-27 1995-05-24 Rolls Royce Plc Organes munis de passages.

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
CH494896A (de) * 1968-08-09 1970-08-15 Sulzer Ag Halterung von Laufschaufeln im Rotor einer Turbomaschine
US3666376A (en) * 1971-01-05 1972-05-30 United Aircraft Corp Turbine blade damper
US3709631A (en) * 1971-03-18 1973-01-09 Caterpillar Tractor Co Turbine blade seal arrangement
BE791375A (fr) * 1971-12-02 1973-03-01 Gen Electric Deflecteur et amortisseur pour ailettes de turbomachines
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4280795A (en) * 1979-12-26 1981-07-28 United Technologies Corporation Interblade seal for axial flow rotary machines
US4347040A (en) * 1980-10-02 1982-08-31 United Technologies Corporation Blade to blade vibration damper
FR2517779B1 (fr) * 1981-12-03 1986-06-13 Snecma Dispositif d'amortissement des aubes d'une soufflante de turbomachine
US4455122A (en) * 1981-12-14 1984-06-19 United Technologies Corporation Blade to blade vibration damper
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
JPS6022002A (ja) * 1983-07-18 1985-02-04 Hitachi Ltd タ−ボ機械の翼構造
US4505642A (en) * 1983-10-24 1985-03-19 United Technologies Corporation Rotor blade interplatform seal
US4568247A (en) * 1984-03-29 1986-02-04 United Technologies Corporation Balanced blade vibration damper
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper
US5261790A (en) * 1992-02-03 1993-11-16 General Electric Company Retention device for turbine blade damper
US5313786A (en) * 1992-11-24 1994-05-24 United Technologies Corporation Gas turbine blade damper
US5415526A (en) * 1993-11-19 1995-05-16 Mercadante; Anthony J. Coolable rotor assembly

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2413542A1 (fr) * 1977-12-28 1979-07-27 Gen Electric Amortisseur d'aube de turbomachine
DE3236021A1 (de) * 1981-11-10 1983-05-19 BBC Aktiengesellschaft Brown, Boveri & Cie., 5401 Baden, Aargau Mit schaufeln versehener turbinenrotorkoerper
FR2712629A1 (fr) * 1983-07-27 1995-05-24 Rolls Royce Plc Organes munis de passages.
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
WO1994012772A1 (fr) * 1992-11-24 1994-06-09 United Technologies Corporation Joint d'etancheite pour aubes d'une turbine a gaz

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2055898A2 (fr) * 2007-11-02 2009-05-06 United Technologies Corporation Aube de turbine dotée de refroidissement de plate-forme
EP2055898A3 (fr) * 2007-11-02 2012-10-31 United Technologies Corporation Aube de turbine dotée de refroidissement de plate-forme
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Also Published As

Publication number Publication date
AU3913495A (en) 1996-06-20
JP3789153B2 (ja) 2006-06-21
EP0717170B1 (fr) 1999-03-10
DE69508201D1 (de) 1999-04-15
US5513955A (en) 1996-05-07
DE69508201T2 (de) 1999-10-14
JPH08232601A (ja) 1996-09-10
AU704412B2 (en) 1999-04-22

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